CN110360900A - Launch Vehicle Ground Support System remote control apparatus - Google Patents
Launch Vehicle Ground Support System remote control apparatus Download PDFInfo
- Publication number
- CN110360900A CN110360900A CN201910584282.7A CN201910584282A CN110360900A CN 110360900 A CN110360900 A CN 110360900A CN 201910584282 A CN201910584282 A CN 201910584282A CN 110360900 A CN110360900 A CN 110360900A
- Authority
- CN
- China
- Prior art keywords
- control
- support system
- remote
- combination
- equipment
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical group C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 32
- 238000004891 communication Methods 0.000 claims abstract description 21
- 238000012544 monitoring process Methods 0.000 claims description 31
- 238000000034 method Methods 0.000 claims description 12
- 230000008569 process Effects 0.000 claims description 8
- 230000009471 action Effects 0.000 claims description 7
- 230000003287 optical effect Effects 0.000 claims description 6
- 238000012546 transfer Methods 0.000 claims description 6
- 238000005070 sampling Methods 0.000 claims description 3
- 238000004088 simulation Methods 0.000 claims 1
- 101100190618 Arabidopsis thaliana PLC3 gene Proteins 0.000 description 14
- 238000013461 design Methods 0.000 description 5
- 230000005540 biological transmission Effects 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000009977 dual effect Effects 0.000 description 2
- 238000012905 input function Methods 0.000 description 2
- 230000002159 abnormal effect Effects 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000004886 process control Methods 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 210000001113 umbilicus Anatomy 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/01—Arrangements thereon for guidance or control
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- Selective Calling Equipment (AREA)
Abstract
A kind of Launch Vehicle Ground Support System remote control apparatus, front-end control unit, front end display unit, data acquisition unit and power distribution unit including being located at front end；Positioned at the remote control unit, emergency flight control unit and remote display unit of rear end equipment；And the communication equipment of both connections.The device can be realized the remote auto control to transmitting support system, while manually control link automatically controlling to additionally provide except link, further improve the mission reliability of system.
Description
Technical field
The present invention relates to field of aerospace, in particular to a kind of Launch Vehicle Ground Support System remotely controls dress
It sets.
Background technique
Launch Vehicle Ground Support System, which refers to, to be completed rocket transhipment, plays launching site equipment after perpendicular, filling and igniting
The facility of protection.
Currently, improving tranmitting frequency, China opens in private space launch field at present to reduce the requirement to transmitter site
Begin to execute launch mission using " three is flat " (horizontal general assembly, horizontal checkout and horizontal transported erect transmitting) mode, in this mode
Under, consider that for system requirements since filling, launching site is at unattended full-automatic emitting shape based on personnel risk is reduced
State, all field devices are monitored and are controlled by long-range control combination, once rocket occur fails the case where lighting a fire as scheduled,
It can be released with remote auto control propellant, terminate transmitting process.
This emission mode also proposed very high requirement to the reliability of transmitting support system and its remote control equipment,
Because at this moment fuel oil has filled, if since the failure of transmitting support system causes transmitting to delay or fail, bring wind
Danger and loss are all very big.
The raising of equipment dependability at present relies primarily on the guarantee of raising and the reliability test verifying of component grade, this
The cost of equipment can be made to greatly increase, and in this way, after the raising of reliability reaches a certain level, be difficult to mention again
Gao Liao.Emit support system as a kind of transmitting and ensures equipment, under the major premise for reducing overall emission cost, equipment dependability
It is required that raising and cost control between generate contradiction, this contradiction is always the main barrier of space product high-volume civil nature
Hinder.
Summary of the invention
In view of the deficiencies of the prior art, it is remote to provide a kind of carrier rocket transmitting support system based on Redundancy Design for the disclosure
Process control device, while above-mentioned remote control requirements of realization " three the is flat " emission mode to transmitting support system, Ke Yi
In the case where increasing limited cost, it is obviously improved the mission reliability of transmitting support system.
The disclosure provides a kind of Launch Vehicle Ground Support System remote control apparatus, including headend equipment and rear end
The communication equipment of both equipment, and connection；Wherein,
Headend equipment includes: that front-end control unit, front end display unit, data acquisition unit and power distribution unit, rear end are set
Standby includes: remote control unit, emergency flight control unit and remote display unit；
Front-end control unit is used to control the operations of transmitting support system by the front end display unit in front end,
The data acquisition unit is used to acquire the data information of transmitting support system, and is sent to front end through front and back ends control unit
It is shown with remote display unit；
Remote control unit is used to control the operations of transmitting support system by the remote display unit in rear end,
The emergency flight control unit is sent out for directly sending control instruction to the front-end control unit so that described control unit controls
It penetrates support system and executes corresponding operating；
Power distribution unit supports system power for completing transmitting.
Preferably, front-end control unit includes electrical control combination 1, PLC3 and control executing agency 4, front end display unit
Interface 6 is monitored and automatically controlled including front end, and data acquisition unit includes data sampling sensor 5, and power distribution unit includes motor
Control combination 2, in which:
The electrical control combination 1 is combined for computer, with the front end display unit, data acquisition unit and PLC3 phase
Even, for completing the data acquisition of transmitting support system and uploading, the input/output of digital quantity analog quantity is controlled, and distal end
The reception of control instruction and front end automatic control function；
The PLC3 receives the control instruction from electrical control combination 1 or emergency flight control unit, controls the control
Executing agency 4 processed completes control output；
The front end monitoring and automatic control interface 6 are display and the input terminal of electrical control combination 1, are used for
The data that transmitting support system is completed in front end are shown, process monitors and instruction input；
The motor control combination 2 provides respectively required power supply for transmitting support system subsystems and equipment,
Partially manual control and emergency-off function are provided simultaneously.
Preferably, the remote control unit includes long-range control combination 8, and emergency flight control unit includes emergency flight control panel
9, remote display unit includes remote monitoring and automatic control interface 10, in which:
The long-range control combination 8 is computer combination, communication equipment by end equipment before and after the connection and electrical
Control combination 1 is connected, the main automatic control for completing transmitting support system and long-range monitoring；
The emergency flight control panel 9 provides manual control button, includes compiling of instruction and remote transmitting device, by described
The communication equipment of connection front and back end equipment is connected with PLC3, directly can send control instruction to PLC3 when pressing lower button；
The remote monitoring and automatic control interface 10 are display and the input terminal of the long-range control combination 8, are used for
The data that completion emits support system in distal end are shown, process monitors and instruction input.
Preferably, the communication equipment for connecting the front and back end equipment is the network switch, serial ports, CAN 1553B bus
One of.
Preferably, the communication equipment includes back-end network interchanger 11 and front network interchanger 7, the long-range control
Before combination 8 and emergency flight control panel 9 are connected to through the back-end network interchanger 11, optical cable and front network interchanger 7 respectively
1 and PLC3 is combined in the electrical control at end.
Preferably, the long-range control combination 8 is the portable computer for including the port DI, DO and bus data transfer card
Combination completes transmitting and supports system remote monitoring and automatically control for running transmitting support system far-end monitoring system software.
Preferably, it includes DI, DO, AD, DA, serial communication card and bus data transfer card that the electrical control, which combines 1 to be,
Computer combination, for run transmitting support system front end Control System Software, complete front-end control system data acquisition
With upload, digital quantity analog quantity output and input control, remote control instruction reception and front end automatic control function.
Preferably, the Launch Vehicle Ground Support System remote control apparatus further includes video monitoring equipment, is used
In the monitoring when issuing control instruction by the emergency flight control unit to transmitting support system relevant device action situation.
Preferably, the video monitoring equipment includes the video capture device and the indoor video of monitoring for being mounted on launching site
Display terminal.
As it can be seen that on the one hand provide staff by front end display unit emits support system in front-end operations to the present apparatus
Control instruction input function, on the other hand by remote display unit and remote control unit provide personnel withdraw it is right behind front end
Emit the remote auto control function of support system；It is also mentioned except 8 → 11 → 7 → 1 → 3 → 4 automatic control link simultaneously
9 → 11 → 7 → 3 → 4 have been supplied to manually control link, this manually controls link and avoids long-range control combination and electrical control combination
Two lower complex components of reliability, reliability itself is higher, and dual redundant design in this way can further increase hair
Penetrate the mission reliability for supporting system remote control device or even entire transmitting support system.Compared with prior art, the disclosure
Beneficial effect be: the front-end control and remote auto control to Launch Vehicle Ground Support System can be completed, simultaneously
By the Redundancy Design of control instruction transmission link, the mission reliability of system is improved.
Detailed description of the invention
Disclosure exemplary embodiment is described in more detail in conjunction with the accompanying drawings, the disclosure it is above-mentioned and other
Purpose, feature and advantage will be apparent, wherein in disclosure exemplary embodiment mode, identical reference label
Typically represent same parts.
The composition and signal of the Launch Vehicle Ground Support System remote control apparatus of Fig. 1 display example embodiment
Move towards schematic diagram.
The Launch Vehicle Ground Support System remote control apparatus course of work of Fig. 2 display example embodiment is illustrated
Figure.
Specific embodiment
Preferred embodiment of the present disclosure is more fully described below with reference to accompanying drawings.Although showing the disclosure in attached drawing
Preferred embodiment, however, it is to be appreciated that may be realized in various forms the disclosure without that should be limited by embodiments set forth here
System.On the contrary, thesing embodiments are provided so that the disclosure is more thorough and complete, and can be complete by the scope of the present disclosure
Ground is communicated to those skilled in the art.
The composition of the Launch Vehicle Ground Support System remote control apparatus of exemplary embodiment is given in attached drawing 1
Figure, comprising: set positioned at the rear end equipment in monitoring hall and positioned at the communication of both the headend equipment of launching site, and connection
It is standby.Wherein,
Headend equipment includes: front-end control unit, front end display unit, data acquisition unit and power distribution unit.Its front end
Control unit is used for the operations in front end by front end display unit control transmitting support system；Data acquisition unit is used for
The data information of acquisition transmitting support system, and front end is sent to through front and back ends control unit and remote display unit is shown；Match
Electric unit supports system power for completing transmitting.
Rear end equipment includes: remote control unit, emergency flight control unit and remote display unit.Its remote control unit is used
In the operations for controlling transmitting support system by remote display unit in rear end；Emergency flight control unit is used for directly to described
Front-end control unit sends control instruction, executes corresponding operating so that described control unit controls transmitting support system.
Preferably, the front-end control unit in the present embodiment includes electrical control combination 1, PLC3 and control
Executing agency 4, front end display unit include front end monitoring and automatically control interface 6, and data acquisition unit includes that data acquisition passes
Sensor 5, power distribution unit include motor control combination 2, in which:
Electrical control combination 1 is combined for computer, is connected with front end display unit, data acquisition unit and PLC3, is used for
It completes the data acquisition of transmitting support system and uploads, the input/output control and remote control instruction of digital quantity analog quantity
Reception and front end automatic control function；
PLC3 receives the control instruction from electrical control combination 1 or emergency flight control unit, controls the control execution machine
Structure 4 completes control output；
Front end monitoring and automatic control interface 6 are display and the input terminal of electrical control combination 1, for completing in front end
The data of transmitting support system are shown, process monitors and instruction input；
Motor control combination 2 provides respectively required power supply for transmitting support system subsystems and equipment, simultaneously
Partially manual control and emergency-off function are provided.The combination also may include wireless control module, realize in case of emergency
Realize that system cut-off is supported in transmitting by remotely controlling.
Preferably, the remote control unit in the present embodiment includes long-range control combination 8, emergency flight control list
Member includes emergency flight control panel 9, and remote display unit includes remote monitoring and automatic control interface 10.Wherein:
Long-range control combination 8 is computer combination, and the communication equipment by connection front and back end equipment combines 1 with electrical control
It is connected, the main automatic control for completing transmitting support system and long-range monitoring；
Emergency flight control panel 9 provides manual control button, includes compiling of instruction and remote transmitting device, by connection front and back
The communication equipment of end equipment is connected with PLC3, directly can send control instruction to PLC3 when pressing lower button；
Remote monitoring and automatic control interface 10 are display and the input terminal of long-range control combination 8, for complete in distal end
At the data of transmitting support system are shown, process monitors and instruction input.
In the disclosure, connect the front and back end equipment communication equipment can be the network switch, serial ports, CAN or
One of 1553B bus.
Preferably, communication equipment includes back-end network interchanger 11 and front network exchange in the present embodiment
Machine 7, long-range control combination 8 and emergency flight control panel 9 are respectively through back-end network interchanger 11, optical cable and front network interchanger 7
1 and PLC3 is combined in the electrical control for being connected to front end.
Preferably, long-range control combination 8 is include the port DI, DO and bus data transfer card portable
Computer combination, for run transmitting support system far-end monitoring system software, complete transmitting support system remote monitoring and from
Dynamic control.
Preferably, it includes DI, DO, AD, DA, serial communication card and bus data that electrical control, which combines 1 to be,
The computer of transmission card combines, and supports system front end Control System Software for running transmitting, completes the number of front-end control system
Function is automatically controlled according to output and input control, the reception of remote control instruction and the front end of acquisition and upload, digital quantity analog quantity
Energy.
In addition, the Launch Vehicle Ground Support System remote control apparatus in the present embodiment can also include that video is supervised
Equipment is controlled, is used for when issuing control instruction by the emergency flight control unit to transmitting support system relevant device action situation
Monitoring.It specifically includes the video capture device for being mounted on launching site and monitors indoor video display terminal.
The Launch Vehicle Ground Support System remote control apparatus work of exemplary embodiment is given in attached drawing 1
Signal flow in the process:
The control instruction that long-range control combination 8 issues is transmitted to by back-end network interchanger 11, optical cable and preceding end switch 7
Front end electrical control combination 1, it is defeated that electrical control combination 1 controls all kinds of completion of control executing agencies 4 controls by front end PLC3 again
Out；
Front end electrical control combination 1 collects the state of the various kinds of sensors 5 at scene and location information passes through front network
Interchanger 7, optical cable and rear end switch 11 are transmitted to long-range control combination 8, and real-time display automatically controls interface 10 in distal end；
The control instruction that emergency flight control panel 9 issues is transmitted to by back-end network interchanger 11, optical cable and preceding end switch 7
PLC3 controls all kinds of control executing agencies 4 and completes control output.
For example, distribution system can be fitted to each other with the PLC in, emergency flight control panel and headend equipment, to provide
Triplex level redundancy protection.Specifically, on the one hand, rear end equipment directly can send command information to PLC by communication module, thus
PLC directly controls relevant device and terminates current operation.And the equipment being terminated can acquire information simultaneously by data sampling sensor
It is transmitted directly to the receiver of distribution system, so that the controller of distribution system judges according to the information, the operation of above equipment
Whether it has been terminated.When the operation of above equipment is not terminated, the controller of distribution system can control the device powers down,
The movement of termination device in a manner of through power-off provides further redundancy protecting for rocket secure transmission.
Further, emergency flight control panel can send signal directly to distribution system, and distribution system passes through its controller
Equipment directly is corresponded to rocket launching current action and carries out power-off protection.Correspondingly, distribution system can pass through its controller point
It is not electrically connected the electric switch of each transmitting holding equipment.Multiple emergency buttons, each emergency button point can be set in rear end equipment
Different rocket launching is not corresponded to and supports system equipment, for example, it is 2,3 ... that these buttons, which can mark, these numbers are successively
Corresponding corresponding holding equipment, controller distinguish holding equipment to be powered off according to number, preferably avoid the mistake of distribution system
Power blackout situation.
Attached drawing 2 gives the worked of Launch Vehicle Ground Support System remote control apparatus in exemplary embodiment
Journey.
As shown in Fig. 2, after rocket is transported to launching site, transmitting support system start execute transhipment erector leveling,
Rocket is perpendicular, transmitting station leveling, rocket transfers to transmitting station, folded arm is opened, lock wind-proof device and vertical arm is fallen in advance etc., these
The implementation procedure of work is all made of the mode of staff scene guarantee, and personnel can be monitored at the scene by front end and automatic control
6 input control of interface instruction processed, intervenes control flow manually at any time.
Later, since secondary leveling after rocket filling, it is in unattended state, into distance control mode, at this moment
From secondary leveling, to release wind-proof device, again to rocket take off posterior umbilicus armed fastly fall etc. control actions by long-range control combination 8
Automatically it sequentially completes.Since the stage rocket has completed repropellenting, transmitting supports system remote control equipment event occur
Hinder and lead to the risk of abortive launch and lose very big, therefore manual Redundant Control measure is increased to these three control actions: 8
When → 11 → 7 → 1 → 3 → 4 automatic control link breaks down, it can be manually controlled under link by 9 → 11 → 7 → 3 → 4
Control instruction is sent out, control function is completed.It, can be from emergency flight control face i.e. once finding the abnormal conditions that control instruction cannot be assigned
Plate issues emergency flight control instruction.
It is relatively independent between each movement needed to be implemented due to transmitting support system, in order to improve fault condition
Under treatment effeciency, the present embodiment respectively corresponds every by the way of multiple Action Buttons are arranged on emergency flight control panel 9
The movement that a long-range control of needs executes automatically controls link and goes to that failure occurs in which movement, just in emergency flight control face
Which button is pressed on plate 9, and instruction is re-emitted by the higher link that manually controls of reliability.It can also only setting one press
Button obtains the movement being presently in by the communication between emergency flight control panel 9 and long-range control combination 8 after a button pressed automatically
Stage, and then assign command adapted thereto.
On the one hand the present apparatus is monitored by front end and automatic control interface 6 provides staff and emits branch in front-end operations
The control instruction input function of system is held, on the other hand by remote monitoring and automatic control interface 10 and 8 institute of long-range control combination
Remote control unit provide personnel and withdraw the transmitting behind front end and support system remote automatic control function, while also 8
9 → 11 → 7 → 3 → 4 are provided except → 11 → 7 → 1 → 3 → 4 automatic control link and manually controls link, this is manually controlled
Link avoids long-range control combination and two lower complex components of reliability are combined in electrical control, reliability itself is higher；
Dual redundant design in this way can significantly improve transmitting and system remote control device or even entire transmitting is supported to support system
The mission reliability of system.Compared with prior art, the beneficial effect of the disclosure is: can complete the front end control of transmitting support system
System and remote auto control, while passing through the Redundancy Design of control instruction transmission link, improve the mission reliability of system.
Above-mentioned technical proposal is exemplary embodiment of the present invention, for those skilled in the art, at this
On the basis of disclosure of the invention application method and principle, it is easy to make various types of improvement or deformation, be not limited solely to this
Method described in above-mentioned specific embodiment is invented, therefore previously described mode is only preferred, and it is not restrictive
Meaning.
Claims (9)
1. a kind of Launch Vehicle Ground Support System remote control apparatus, which is characterized in that including headend equipment and rear end
The communication equipment of both equipment, and connection；
Wherein headend equipment includes: that front-end control unit, front end display unit, data acquisition unit and power distribution unit, rear end are set
Standby includes: remote control unit, emergency flight control unit and remote display unit；
The front-end control unit is used to control the operations of transmitting support system by the front end display unit in front end,
The data acquisition unit is used to acquire the data information of transmitting support system, and is sent to front end through front and back ends control unit
It is shown with remote display unit；
The remote control unit is used to control the operations of transmitting support system by the remote display unit in rear end,
The emergency flight control unit is sent out for directly sending control instruction to the front-end control unit so that described control unit controls
It penetrates support system and executes corresponding operating；
The power distribution unit supports system power for completing transmitting.
2. Launch Vehicle Ground Support System remote control apparatus according to claim 1, which is characterized in that described
Front-end control unit includes electrical control combination (1), PLC (3) and control executing agency (4)；
The front end display unit includes front end monitoring and automatically controls interface (6)；
The data acquisition unit includes data sampling sensor (5)；
The power distribution unit includes motor control combination (2)；
Wherein, the electrical control combination (1) is computer combination, with the front end display unit, data acquisition unit and PLC
(3) it is connected, for completing the data acquisition of transmitting support system and uploading, the input/output of digital quantity analog quantity is controlled, and
The reception of remote control instruction and front end automatic control function；
The PLC (3) receives the control instruction from electrical control combination (1) or emergency flight control unit, controls the control
Executing agency (4) processed completes control output；
The front end monitoring and automatic control interface (6) are display and the input terminal that (1) is combined in the electrical control, are used for
The data that transmitting support system is completed in front end are shown, process monitors and instruction input；
The motor control combination (2) provides respectively required power supply for transmitting support system subsystems and equipment, together
When provide it is partially manual control and emergency-off function.
3. Launch Vehicle Ground Support System remote control apparatus according to claim 2, which is characterized in that described
Remote control unit includes long-range control combination (8), and emergency flight control unit includes emergency flight control panel (9), remote display unit
Including remote monitoring and automatically control interface (10), wherein
The long-range control combination (8) is computer combination, by the communication equipment and electric-controlled of end equipment before and after the connection
System combination (1) is connected, the main automatic control for completing transmitting support system and long-range monitoring；
The emergency flight control panel (9) provides manual control button, includes compiling of instruction and remote transmitting device, by the company
The communication equipment for connecing front and back end equipment is connected with PLC (3), directly can send control instruction to PLC (3) when pressing lower button；
The remote monitoring and automatic control interface (10) are display and the input terminal of the long-range control combination (8), are used for
The data that completion emits support system in distal end are shown, process monitors and instruction input.
4. Launch Vehicle Ground Support System remote control apparatus according to claim 1, which is characterized in that connection
The communication equipment of the front and back end equipment is one of the network switch, serial ports, CAN 1553B bus.
5. Launch Vehicle Ground Support System remote control apparatus according to claim 4, which is characterized in that described
Communication equipment includes back-end network interchanger (11) and front network interchanger (7), and the long-range control combination (8) and emergency are controlled
Panel (9) processed is connected to the described of front end through the back-end network interchanger (11), optical cable and front network interchanger (7) respectively
(1) and PLC (3) are combined in electrical control.
6. Launch Vehicle Ground Support System remote control apparatus according to claim 3, which is characterized in that described
Long-range control combination (8) is the portable computer combination for including the port DI, DO and bus data transfer card, for running transmitting
Support system far-end monitoring system software completes transmitting and supports system remote monitoring and automatically control.
7. Launch Vehicle Ground Support System remote control apparatus according to claim 2, which is characterized in that described
Electrical control combination (1) is the computer combination for including DI, DO, AD, DA, serial communication card and bus data transfer card, is used for
System front end Control System Software is supported in operation transmitting, is completed the data acquisition of front-end control system and is uploaded, digital quantity simulation
Amount outputs and inputs control, the reception of remote control instruction and front end automatic control function.
8. Launch Vehicle Ground Support System remote control apparatus according to claim 1, which is characterized in that also wrap
Video monitoring equipment is included, is used for when issuing control instruction by the emergency flight control unit to transmitting support system relevant device
The monitoring of action situation.
9. Launch Vehicle Ground Support System remote control apparatus according to claim 8, which is characterized in that described
Video monitoring equipment includes the video capture device and the indoor video display terminal of monitoring for being mounted on launching site.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910584282.7A CN110360900A (en) | 2019-07-01 | 2019-07-01 | Launch Vehicle Ground Support System remote control apparatus |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910584282.7A CN110360900A (en) | 2019-07-01 | 2019-07-01 | Launch Vehicle Ground Support System remote control apparatus |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110360900A true CN110360900A (en) | 2019-10-22 |
Family
ID=68217848
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910584282.7A Pending CN110360900A (en) | 2019-07-01 | 2019-07-01 | Launch Vehicle Ground Support System remote control apparatus |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110360900A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110780599A (en) * | 2019-11-01 | 2020-02-11 | 北京航天自动控制研究所 | Dynamic test launch control system of carrier rocket |
| CN112556514A (en) * | 2020-12-08 | 2021-03-26 | 北京航天发射技术研究所 | Remote state monitoring system for heavy carrier rocket launching support equipment |
| CN113904727A (en) * | 2021-09-22 | 2022-01-07 | 北京电子工程总体研究所 | Remote control system and method for display and control console of command and control vehicle |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101782754A (en) * | 2009-12-30 | 2010-07-21 | 北京宇航系统工程研究所 | Redundancy switching circuit used for ground test launch and control system of carrier rocket |
| CN102915029A (en) * | 2012-10-15 | 2013-02-06 | 中国运载火箭技术研究院 | Avionics system automatic test platform based on reusable spacecraft |
| CN102997761A (en) * | 2012-12-17 | 2013-03-27 | 北京航空航天大学 | Control system of solid-liquid dynamic sounding rocket |
| CN203385331U (en) * | 2013-07-30 | 2014-01-08 | 上海航天测控通信研究所 | Rocket ground monitoring system |
| CN103822539A (en) * | 2014-03-24 | 2014-05-28 | 上海航天电子通讯设备研究所 | Rocket ground test control system based on redundant structure |
| CN109066976A (en) * | 2018-08-08 | 2018-12-21 | 上海宇航系统工程研究所 | Autonomous distribution control device on a kind of carrier rocket arrow |
| CN109870070A (en) * | 2019-03-01 | 2019-06-11 | 北京星际荣耀空间科技有限公司 | A kind of integrated wireless launch vehicle measurement applied to Solid Launch Vehicle |
| CN210400199U (en) * | 2019-07-01 | 2020-04-24 | 蓝箭航天空间科技股份有限公司 | Remote control device for ground launch support system of carrier rocket |
-
2019
- 2019-07-01 CN CN201910584282.7A patent/CN110360900A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101782754A (en) * | 2009-12-30 | 2010-07-21 | 北京宇航系统工程研究所 | Redundancy switching circuit used for ground test launch and control system of carrier rocket |
| CN102915029A (en) * | 2012-10-15 | 2013-02-06 | 中国运载火箭技术研究院 | Avionics system automatic test platform based on reusable spacecraft |
| CN102997761A (en) * | 2012-12-17 | 2013-03-27 | 北京航空航天大学 | Control system of solid-liquid dynamic sounding rocket |
| CN203385331U (en) * | 2013-07-30 | 2014-01-08 | 上海航天测控通信研究所 | Rocket ground monitoring system |
| CN103822539A (en) * | 2014-03-24 | 2014-05-28 | 上海航天电子通讯设备研究所 | Rocket ground test control system based on redundant structure |
| CN109066976A (en) * | 2018-08-08 | 2018-12-21 | 上海宇航系统工程研究所 | Autonomous distribution control device on a kind of carrier rocket arrow |
| CN109870070A (en) * | 2019-03-01 | 2019-06-11 | 北京星际荣耀空间科技有限公司 | A kind of integrated wireless launch vehicle measurement applied to Solid Launch Vehicle |
| CN210400199U (en) * | 2019-07-01 | 2020-04-24 | 蓝箭航天空间科技股份有限公司 | Remote control device for ground launch support system of carrier rocket |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110780599A (en) * | 2019-11-01 | 2020-02-11 | 北京航天自动控制研究所 | Dynamic test launch control system of carrier rocket |
| CN112556514A (en) * | 2020-12-08 | 2021-03-26 | 北京航天发射技术研究所 | Remote state monitoring system for heavy carrier rocket launching support equipment |
| CN113904727A (en) * | 2021-09-22 | 2022-01-07 | 北京电子工程总体研究所 | Remote control system and method for display and control console of command and control vehicle |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110360900A (en) | Launch Vehicle Ground Support System remote control apparatus | |
| CN109808705B (en) | System for remotely controlling driving | |
| CN101782754B (en) | Redundancy switching circuit used for ground test launch and control system of carrier rocket | |
| CN112947358B (en) | Vehicle-mounted comprehensive test system and method for testing mobile launching satellite | |
| CN102862917B (en) | Telescopic remote control operation device and system for single-cylinder pin-inserting-type crane jibs and crane | |
| CN108266187B (en) | Remote starting device and remote starting control method for coal mining machine | |
| US20110062787A1 (en) | Intelligent Solar Energy Collection System | |
| CN103269130A (en) | Method for remotely confirming remote-control operation of transformer station | |
| CN112066798B (en) | Solid rocket wireless measurement, launch, control, power supply and distribution and safety control system | |
| CN106204829B (en) | Lockset wireless control system and method | |
| WO2019179289A1 (en) | Electric vehicle dual-mode charging system and method | |
| CN104296596A (en) | Carrier rocket testing and launch control procedure command system and method | |
| CN210400199U (en) | Remote control device for ground launch support system of carrier rocket | |
| CN104124077A (en) | Electric switching-on device and switch inversing system of electrical equipment | |
| CN109873496A (en) | High pressure takes control cable and high pressure takes control cable system | |
| CN103475103B (en) | A kind of for distribution tele-control system | |
| CN110287050B (en) | Grid rudder autonomous power distribution time sequence control device | |
| CN105703480A (en) | Transformer neutral point switch remote comprehensive control circuit | |
| CN205989667U (en) | A kind of charging pile | |
| CN110989436B (en) | Networked ground power supply control take-off system of unmanned aerial vehicle | |
| CN201750206U (en) | Conversion device for main control station and non-main control station of DC control system | |
| CN100493992C (en) | Test device for testing additive center tank (ACT) of aircraft | |
| CN103123244A (en) | 57mm digitalized figure antiaircraft gun system | |
| CN202009518U (en) | Stage control system for DMX512 intelligent distribution isolation amplifier | |
| CN106484443B (en) | Train operation program updating device and ground server |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |